34832 Federal Register / Vol. 63, No. 123 / Friday, June 26, 1998 / Proposed Rules

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–166–AD]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–9–80 Series

Airplanes, and Model MD–88 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain McDonnell Douglas Model DC–

9–80 series airplanes, and Model MD–

88 airplanes. This proposal would

require a one-time inspection to detect

corrosion of the lug bores and the

surface of the hinge plates of the

vertical-to-horizontal stabilizer; and

corrective actions, if necessary. This

proposal is prompted by reports of

corrosion of the lug bores and the

surface of the hinge plates of the

vertical-to-horizontal stabilizer,

apparently due to the improper

brushing of cadmium on the hinge

plates during manufacture. The actions

specified by the proposed AD are

intended to detect and correct corrosion

of the lug bores and the surface of the

hinge plates of the vertical-to-horizontal

stabilizer, which could result in reduced

structural integrity of the airplane.

DATES: Comments must be received by

August 10, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

166–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

The Boeing Company, Douglas Products

Division, 3855 Lakewood Boulevard,

Long Beach, California 90846,

Attention: Technical Publications

Business Administration, Dept. C1–L51

(2–60). This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Transport Airplane

Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California.

FOR FURTHER INFORMATION CONTACT:

Brent Bandley, Aerospace Engineer,

Airframe Branch, ANM–120L, FAA,

Transport Airplane Directorate, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California 90712–4137; telephone (562)

627–5237; fax (562) 627–5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 98–NM–166–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

98–NM–166–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports of

corrosion on the lug bores and the

surface of the hinge plates of the

vertical-to-horizontal stabilizer on

certain McDonnell Douglas Model DC–

9–80 series airplanes, and Model MD–

88 airplanes. This corrosion occurred on

airplanes that had accumulated between

15,000 and 30,000 total flight hours.

Investigation has revealed that the hinge

plates were apparently brushed with

cadmium during the assembly drill out

and line ream processes. During these

manufacturing processes, it appears that

the cadmium material became trapped

between the mating hinge plates.

Consequently, chemical action caused

corrosion to occur around the lug bores.

The corrosion has been attributed to the

cadmium-brushed plates, which were

not part of the approved type design.

Such corrosion, if not detected and

corrected in a timely manner, could

result in reduced structural integrity of

the airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

McDonnell Douglas Service Bulletin

MD80–55–054, dated March 3, 1998,

which describes procedures for a onetime visual inspection to detect

corrosion of the lug bores and the

surface of the hinge plates of the

vertical-to-horizontal stabilizer; and

corrective actions, if necessary.

Corrective actions include removal of

corrosion that is within the limits

specified in the Structural Repair

Manual; and replacement of the hinge

plates with new parts, if the corrosion

exceeds the limits specified in the

Structural Repair Manual.

Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

require a one-time inspection to detect

corrosion of the lug bores and the

surface of the hinge plates of the

vertical-to-horizontal stabilizer; and

corrective actions, if necessary. The

proposed AD also would require that

operators report results of inspection

findings (positive or negative) to the

FAA.

Cost Impact

There are approximately 1,059

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

706 airplanes of U.S. registry would be

affected by this proposed AD. It would

take approximately 117 work hours per

airplane (which includes removal and

installation) to accomplish the proposed

inspection, at an average labor rate of

$60 per work hour. Based on these

figures, the cost impact of the proposed

AD on U.S. operators is estimated to be

$4,956,120, or $7,020 per airplane.
Federal Register / Vol. 63, No. 123 / Friday, June 26, 1998 / Proposed Rules 34833

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

Regulatory Impact

The regulations proposed herein

would not have substantial direct effects

on the States, on the relationship

between the national government and

the States, or on the distribution of

power and responsibilities among the

various levels of government. Therefore,

in accordance with Executive Order

12612, it is determined that this

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, will not have a significant

economic impact, positive or negative,

on a substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend part

39 of the Federal Aviation Regulations

(14 CFR part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

McDonnell Douglas: Docket 98–NM–166–

AD.

Applicability: Model DC–9–81 (MD–81),

DC–9–82 (MD–82), DC–9–83 (MD–83), and

DC–9–87 (MD–87) series airplanes, and

Model MD–88 airplanes; as listed in

McDonnell Douglas Service Bulletin MD80–

55–054, dated March 3, 1998; certificated in

any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (c) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To detect and correct corrosion of the lug

bores and the surface of the hinge plates of

the vertical-to-horizontal stabilizer, which

could result in reduced structural integrity of

the airplane, accomplish the following:

(a) Within 18 months after the effective

date of this AD, perform a one-time visual

inspection to detect corrosion of the lug bores

and the surface of the hinge plates of the

vertical-to-horizontal stabilizer, in

accordance with McDonnell Douglas Service

Bulletin MD80–55–054, dated March 3, 1998.

(1) Condition 1: If no corrosion is detected,

no further action is required by this

paragraph.

(2) Condition 2: If any corrosion is detected

that is within the limits specified in the

Structural Repair Manual, prior to further

flight, remove the corrosion in accordance

with the service bulletin.

(3) Condition 3: If any corrosion is detected

that exceeds the limits specified in the

Structural Repair Manual, prior to further

flight, replace the hinge plates with new

parts, in accordance with the service bulletin.

(b) Within 10 days after accomplishing the

inspection required by paragraph (a) of this

AD, or within 10 days after the effective date

of this AD, whichever occurs later, submit a

report of the inspection results (both positive

and negative findings) to the Manager, Los

Angeles Aircraft Certification Office (ACO),

FAA, Transport Airplane Directorate, 3960

Paramount Boulevard, Lakewood, California

90712–4137; fax (562) 627–5210. Information

collection requirements contained in this

regulation have been approved by the Office

of Management and Budget (OMB) under the

provisions of the Paperwork Reduction Act of

1980 (44 U.S.C. 3501 et seq.) and have been

assigned OMB Control Number 2120–0056.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Los

Angeles ACO. Operators shall submit their

requests through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Los Angeles ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(d) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Issued in Renton, Washington, on June 19,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–17007 Filed 6–25–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–138–AD]

RIN 2120–AA64

Airworthiness Directives; Cessna

Aircraft Company 180 and 185 Series

Airplanes.

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

supersede Airworthiness Directive (AD)

80–10–01, which is applied to certain

Cessna Aircraft Company 180 and 185

series airplanes that are equipped with

Airglas Engineering Company, Inc.,

(AECI) Model LW3600–180 single

position or Model LW3600–180A two

position fixed penetration wheel ski

installations. AD 80–10–01 currently

requires: modifying the ski bungee

assemblies, safety cables, and check

cables; limiting the maximum airspeed

to 160 knots with skis installed; and

installing an airspeed limitation

placard. The proposed AD would retain

the actions required in AD 80–10–01,

and would require marking the

maximum airspeed limits on the

airspeed indicator; placing a

supplemental airplane flight manual

(AFM) and AFM supplement in the

cockpit; and adding the Cessna Model

180K airplane to the applicability.

Reports that certain airspeeds cause the

skis to rotate into a nose-down position

during flight prompted the AD action.

The actions specified by the proposed

AD are intended to prevent one or both

wheel skis from rotating into a nosedown position during flight, which

could result in loss of control of the

airplane and/or possible airplane

damage during flight or landing

operations.

DATES: Comments must be received on

or before August 24, 1998.